Question 1 - Plot (i) Adiabatic Flame Temperature (Tflame) versus Oxidizer to Fuel (O/F) ratio and (ii) characteristic v

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Question 1 Plot I Adiabatic Flame Temperature Tflame Versus Oxidizer To Fuel O F Ratio And Ii Characteristic V 1 (82.14 KiB) Viewed 35 times

Question 1 - Plot (i) Adiabatic Flame Temperature (Tflame) versus Oxidizer to Fuel (O/F) ratio and (ii) characteristic velocity (c*) versus Oxidizer to Fuel ratio graphs of propellant combinations stated below. Use NASA CEA (chemical equilibrium analysis) to determine plots. . Change your O/F between 1 and 10 with the 0.5 step size. Plot values in the same graph. a. C32H66/GOX b. C32H66/N20 C. C32H66/Al/N20 (with 20% aluminum by mass in the fuel mixture) d. C32H66/Al/N20 (with 40% aluminum by mass in the fuel mixture) e. Compare Tflame and c* values of propellant combinations. Which propellant combination provides better performance? f. Calculate thrust (T), specific impulse (Isp), total impulse (Itot) and average thrust (T) values of propellants plot 0/F versus Isp. Assume you have total mass flow rate (mtot) of 250 grams/seconds with 10 seconds of burn time (th), nc 0.95, nn = 0.97,90 = 9.81 m/s2. You should find heat of formation values of N20 and C32H66 (paraffin wax) from the literature.